Aircraft time lag varying model approximation and controller designing method

Abstract

The invention discloses an aircraft time lag varying model approximation and controller designing method, and aims to solve the technical problem that the existing robust control theory is lack of the design steps and an aircraft controller cannot be directly designed. The technical scheme is as follows: the robust stability solvable condition of a time varying approximation system is given, a closed loop expecting pole fed back by a linear system state is directly utilized for selection, and a given conditional inequality is given to design a feedback matrix directly according to the characteristic that the real part of all closed loop expecting poles are negative numbers. By utilizing the method, the aircraft model containing time lag varying uncertainty are obtained by engineering technicians in the research field during wind tunnel or flight test, and an aircraft controller can be designed directly, so that the technical problem in the current research that only the robust stability inequality is given and the aircraft controller cannot be designed directly is solved.

Description

technical field [0001] The invention relates to a controller design method, in particular to an aircraft time-lag time-varying model approximation and controller design method. Background technique [0002] Aircraft robust control is one of the key topics in the current international aviation research. When designing high-performance aircraft controllers, robust stability and robust control issues must be considered; the actual aircraft model is a very complex nonlinear model with unknown model structure. Differential equations, in order to describe this complex nonlinearity, people usually use wind tunnel and flight tests to obtain test models described by discrete data; in order to reduce risks and reduce test costs, flight maneuver tests are usually carried out according to different altitudes and Mach numbers, so that , there are not many discrete data describing the aircraft test model, and this model is very practical for the aircraft with better static stability. How...

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Problems solved by technology

[0004] In order to overcome the technical deficiency that the existing robust control theory lacks design steps and is difficult to directly design the flight controller, the present invention provides a time-lag time-varying model approximation of an aircraft and a controller design method; the method provides the actual time-lag time-varying system robust The piecewise approximation of the design conditions of the rod stable controller directly uses the closed-loop expected pole selection of the linear system state feedback, and according to the characteristics that the real parts of all the closed-loop expected poles are all negative numbers, the limiting condition inequality is given to directly design the feedback matrix, which can be Directly design the flight controller for the aircraft model with time-lag and time-varying uncertainty obtained from the wind tunnel or flight test, which solves the technical problem that the current research only gives the robust stability inequality and cannot directly design the flight controller

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